U.S. patent number 8,707,673 [Application Number 13/734,156] was granted by the patent office on 2014-04-29 for articulated transition duct in turbomachine.
This patent grant is currently assigned to General Electric Company. The grantee listed for this patent is General Electric Company. Invention is credited to James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Ronnie Ray Pentecost.
United States Patent |
8,707,673 |
Flanagan , et al. |
April 29, 2014 |
Articulated transition duct in turbomachine
Abstract
Turbine systems are provided. A turbine system includes a
transition duct comprising an inlet, an outlet, and a duct passage
extending between the inlet and the outlet and defining a
longitudinal axis, a radial axis, and a tangential axis. The outlet
of the transition duct is offset from the inlet along the
longitudinal axis and the tangential axis. The duct passage
includes an upstream portion and a downstream portion. The upstream
portion extends from the inlet between an inlet end and an aft end.
The downstream portion extends from the outlet between an outlet
end and a head end. The turbine system further includes a joint
coupling the aft end of the upstream portion and the head end of
the downstream portion together. The joint is configured to allow
movement of the upstream portion and the downstream portion
relative to each other about or along at least one axis.
Inventors: |
Flanagan; James Scott
(Simpsonville, SC), McMahan; Kevin Weston (Greer, SC),
LeBegue; Jeffrey Scott (Simpsonville, SC), Pentecost; Ronnie
Ray (Travelers Rest, SC) |
Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company |
Schenectady |
NY |
US |
|
|
Assignee: |
General Electric Company
(Schenectady, NY)
|
Family
ID: |
49513838 |
Appl.
No.: |
13/734,156 |
Filed: |
January 4, 2013 |
Current U.S.
Class: |
60/39.37 |
Current CPC
Class: |
F01D
9/023 (20130101); F05D 2250/713 (20130101); F05D
2250/43 (20130101); F05D 2230/642 (20130101) |
Current International
Class: |
F02C
3/00 (20060101) |
Field of
Search: |
;60/39.37,752-760,796-800 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Wongwian; Phutthiwat
Attorney, Agent or Firm: Dority & Manning, PA
Government Interests
This invention was made with government support under contract
number DE-FC26-05NT42643 awarded by the Department of Energy. The
government has certain rights in the invention.
Claims
What is claimed is:
1. A turbine system, comprising: a transition duct comprising an
inlet, an outlet, and a duct passage extending between the inlet
and the outlet and defining a longitudinal axis, a radial axis, and
a tangential axis, the outlet of the transition duct offset from
the inlet along the longitudinal axis, the radial axis and the
tangential axis, the duct passage comprising an upstream portion
and a downstream portion, the upstream portion extending from the
inlet between an inlet end and an aft end, the downstream portion
extending from the outlet between an outlet end and a head end; a
joint coupling the aft end of the upstream portion and the head end
of the downstream portion together, the joint configured to allow
movement of the upstream portion and the downstream portion
relative to each other about or along at least one axis, wherein
the joint comprises a generally annular contact member and a
generally annular socket member, the contact member movable within
the socket member, the contact member connected to and axially
extending from one of the aft end of the upstream portion and the
head end of the downstream portion, the socket member connoted to
the other of the aft end of the upstream portion and the head end
of the downstream portion; and a turbine section in communication
with the transition duct, the turbine section comprising a first
stage bucket assembly, wherein no nozzles are disposed upstream of
the first stage bucket assembly.
2. The turbine system of claim 1, wherein the joint is configured
to allow movement of the upstream portion and the downstream
portion relative to each other about or along at least two
axes.
3. The turbine system of claim 1, wherein the joint is configured
to allow movement of the upstream portion and the downstream
portion relative to each other about or along three axes.
4. The turbine system of claim 1, wherein the contact member is
mounted to the head end of the downstream portion and the socket
member is mounted to the aft end of the upstream portion.
5. The turbine system of claim 1, wherein the contact member has a
generally curvilinear outer surface.
6. The turbine system of claim 1, wherein the contact member has a
generally arcuate cross-sectional profile.
7. The turbine system of claim 6, wherein the generally arcuate
cross-sectional profile extends along the longitudinal axis.
8. The turbine system of claim 1, wherein the socket member has a
generally curvilinear inner surface.
9. The turbine system of claim 8, wherein the socket member has a
thickness, and wherein the thickness increases along the
longitudinal axis towards the outlet.
10. A turbomachine, comprising: an inlet section; an exhaust
section; a compressor section; a combustor section, the combustor
section comprising: a transition duct comprising an inlet, an
outlet, and a duct passage extending between the inlet and the
outlet and defining a longitudinal axis, a radial axis, and a
tangential axis, the outlet of the transition duct offset from the
inlet along the longitudinal axis, the radial axis and the
tangential axis, the duct passage comprising an upstream portion
and a downstream portion, the upstream portion extending from the
inlet between an inlet end and an aft end, the downstream portion
extending from the outlet between an outlet end and a head end; and
a joint coupling the aft end of the upstream portion and the head
end of the downstream portion together, the joint configured to
allow movement of the upstream portion and the downstream portion
relative to each other about or along at least one axis, wherein
the joint comprises a generally annular contact member and a
generally annular socket member, the contact member movable within
the socket member, the contact member connected to and axially
extending from one of the aft end of the upstream portion and the
head end of the downstream portion, the socket member connected to
the other of the aft end of the upstream portion and the head end
of the downstream portion; and a turbine section in communication
with the transition duct, the turbine section comprising a first
stage bucket assembly, wherein no nozzles are disposed upstream of
the first stage bucket assembly.
11. The turbomachine of claim 10, wherein the joint is configured
to allow movement of the upstream portion and the downstream
portion relative to each other about or along at least two
axes.
12. The turbomachine of claim 10, wherein the joint is configured
to allow movement of the upstream portion and the downstream
portion relative to each other about or along three axes.
13. The turbomachine of claim 10, wherein the contact member is
mounted to the head end of the downstream portion and the socket
member is mounted to the aft end of the upstream portion.
Description
FIELD OF THE INVENTION
The subject matter disclosed herein relates generally to
turbomachines, such as gas turbine systems, and more particularly
to articulated transition ducts, with components movable about at
least one axis relative to each other, in turbomachines.
BACKGROUND OF THE INVENTION
Turbine systems are one example of turbomachines widely utilized in
fields such as power generation. For example, a conventional gas
turbine system includes a compressor section, a combustor section,
and at least one turbine section. The compressor section is
configured to compress air as the air flows through the compressor
section. The air is then flowed from the compressor section to the
combustor section, where it is mixed with fuel and combusted,
generating a hot gas flow. The hot gas flow is provided to the
turbine section, which utilizes the hot gas flow by extracting
energy from it to drive the compressor, an electrical generator,
and other various loads.
The combustor sections of turbine systems generally include tubes
or ducts for flowing the combusted hot gas therethrough to the
turbine section or sections. Recently, combustor sections have been
introduced which include ducts that shift the flow of the hot gas,
such as by accelerating and turning the hot gas flow. For example,
ducts for combustor sections have been introduced that, while
flowing the hot gas longitudinally therethrough, additionally shift
the flow radially or tangentially such that the flow has various
angular components. These designs have various advantages,
including eliminating first stage nozzles from the turbine
sections. The first stage nozzles were previously provided to shift
the hot gas flow, and may not be required due to the design of
these ducts. The elimination of first stage nozzles may reduce
associated pressure drops and increase the efficiency and power
output of the turbine system.
However, the connection of these ducts to turbine sections is of
increased concern. For example, because the ducts do not simply
extend along a longitudinal axis, but are rather shifted off-axis
from the inlet of the duct to the outlet of the duct, thermal
expansion of the ducts can cause undesirable shifts in the ducts
along or about various axes. These shifts can cause stresses and
strains within the ducts, and may cause the ducts to fail.
Accordingly, improved combustor sections for turbomachines, such as
for turbine systems, would be desired in the art. In particular,
combustor sections and transition ducts thereof which allow for and
accommodate thermal growth of the duct would be advantageous.
BRIEF DESCRIPTION OF THE INVENTION
Aspects and advantages of the invention will be set forth in part
in the following description, or may be obvious from the
description, or may be learned through practice of the
invention.
In one embodiment, a turbine system is provided. The turbine system
includes a transition duct comprising an inlet, an outlet, and a
duct passage extending between the inlet and the outlet and
defining a longitudinal axis, a radial axis, and a tangential axis.
The outlet of the transition duct is offset from the inlet along
the longitudinal axis and the tangential axis. The duct passage
includes an upstream portion and a downstream portion. The upstream
portion extends from the inlet between an inlet end and an aft end.
The downstream portion extends from the outlet between an outlet
end and a head end. The turbine system further includes a joint
coupling the aft end of the upstream portion and the head end of
the downstream portion together. The joint is configured to allow
movement of the upstream portion and the downstream portion
relative to each other about or along at least one axis.
These and other features, aspects and advantages of the present
invention will become better understood with reference to the
following description and appended claims. The accompanying
drawings, which are incorporated in and constitute a part of this
specification, illustrate embodiments of the invention and,
together with the description, serve to explain the principles of
the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
A full and enabling disclosure of the present invention, including
the best mode thereof, directed to one of ordinary skill in the
art, is set forth in the specification, which makes reference to
the appended figures, in which:
FIG. 1 is a schematic view of a gas turbine system according to one
embodiment of the present disclosure;
FIG. 2 is a cross-sectional view of several portions of a gas
turbine system according to one embodiment of the present
disclosure;
FIG. 3 is a perspective view of an annular array of transition
ducts according to one embodiment of the present disclosure;
FIG. 4 is a top rear perspective view of a plurality of transition
ducts and associated impingement sleeves according to one
embodiment of the present disclosure;
FIG. 5 is a side perspective view of a transition duct, including
an upstream portion and a downstream portion, according to one
embodiment of the present disclosure;
FIG. 6 is a side perspective view of a downstream portion of a
transition duct according to one embodiment of the present
disclosure;
FIG. 7 is a cross-sectional view of a portion of a transition duct,
including an upstream portion, a downstream portion, and a joint
therebetween, according to one embodiment of the present
disclosure; and,
FIG. 8 is a cross-sectional view of a turbine section of a gas
turbine system according to one embodiment of the present
disclosure.
DETAILED DESCRIPTION OF THE INVENTION
Reference now will be made in detail to embodiments of the
invention, one or more examples of which are illustrated in the
drawings. Each example is provided by way of explanation of the
invention, not limitation of the invention. In fact, it will be
apparent to those skilled in the art that various modifications and
variations can be made in the present invention without departing
from the scope or spirit of the invention. For instance, features
illustrated or described as part of one embodiment can be used with
another embodiment to yield a still further embodiment. Thus, it is
intended that the present invention covers such modifications and
variations as come within the scope of the appended claims and
their equivalents.
FIG. 1 is a schematic diagram of a turbomachine, which in the
embodiment shown is a gas turbine system 10. It should be
understood that the turbine system 10 of the present disclosure
need not be a gas turbine system 10, but rather may be any suitable
turbine system 10, such as a steam turbine system or other suitable
system. Further, it should be understood that a turbomachine
according to the present disclosure need not be a turbine system,
but rather may be any suitable turbomachine. The gas turbine system
10 may include a compressor section 12, a combustor section 14
which may include a plurality of combustors 15 as discussed below,
and a turbine section 16. The compressor section 12 and turbine
section 16 may be coupled by a shaft 18. The shaft 18 may be a
single shaft or a plurality of shaft segments coupled together to
form shaft 18. The shaft 18 may further be coupled to a generator
or other suitable energy storage device, or may be connected
directly to, for example, an electrical grid. An inlet section 19
may provide an air flow to the compressor section 12, and exhaust
gases may be exhausted from the turbine section 16 through an
exhaust section 20 and exhausted and/or utilized in the system 10
or other suitable system, exhausted into the atmosphere, or
recycled through a heat recovery steam generator.
Referring to FIG. 2, a simplified drawing of several portions of a
gas turbine system 10 is illustrated. The gas turbine system 10 as
shown in FIG. 2 comprises a compressor section 12 for pressurizing
a working fluid, which in general is pressurized air but could be
any suitable fluid, that is flowing through the system 10.
Pressurized working fluid discharged from the compressor section 12
flows into a combustor section 14, which may include a plurality of
combustors 15 (only one of which is illustrated in FIG. 2) disposed
in an annular array about an axis of the system 10. The working
fluid entering the combustor section 14 is mixed with fuel, such as
natural gas or another suitable liquid or gas, and combusted. Hot
gases of combustion flow from each combustor 15 to a turbine
section 16 to drive the system 10 and generate power.
A combustor 15 in the gas turbine 10 may include a variety of
components for mixing and combusting the working fluid and fuel.
For example, the combustor 15 may include a casing 21, such as a
compressor discharge casing 21. A variety of sleeves, which may be
axially extending annular sleeves, may be at least partially
disposed in the casing 21. The sleeves, as shown in FIG. 2, extend
axially along a generally longitudinal axis 98, such that the inlet
of a sleeve is axially aligned with the outlet. For example, a
combustor liner 22 may generally define a combustion zone 24
therein. Combustion of the working fluid, fuel, and optional
oxidizer may generally occur in the combustion zone 24. The
resulting hot gases of combustion may flow generally axially along
the longitudinal axis 98 downstream through the combustion liner 22
into a transition piece 26, and then flow generally axially along
the longitudinal axis 98 through the transition piece 26 and into
the turbine section 16.
The combustor 15 may further include a fuel nozzle 40 or a
plurality of fuel nozzles 40. Fuel may be supplied to the fuel
nozzles 40 by one or more manifolds (not shown). As discussed
below, the fuel nozzle 40 or fuel nozzles 40 may supply the fuel
and, optionally, working fluid to the combustion zone 24 for
combustion.
As shown in FIGS. 3 through 7, a combustor 15 according to the
present disclosure may include one or more transition ducts 50. The
transition ducts 50 of the present disclosure may be provided in
place of various axially extending sleeves of other combustors. For
example, a transition duct 50 may replace the axially extending
transition piece 26 and, optionally, the combustor liner 22 of a
combustor 15. Thus, the transition duct may extend from the fuel
nozzles 40, or from the combustor liner 22. As discussed below, the
transition duct 50 may provide various advantages over the axially
extending combustor liners 22 and transition pieces 26 for flowing
working fluid therethrough and to the turbine section 16.
As shown, the plurality of transition ducts 50 may be disposed in
an annular array about a longitudinal axis 90. Further, each
transition duct 50 may extend between a fuel nozzle 40 or plurality
of fuel nozzles 40 and the turbine section 16. For example, each
transition duct 50 may extend from the fuel nozzles 40 to the
turbine section 16. Thus, working fluid may flow generally from the
fuel nozzles 40 through the transition duct 50 to the turbine
section 16. In some embodiments, the transition ducts 50 may
advantageously allow for the elimination of the first stage nozzles
in the turbine section, which may reduce or eliminate any
associated pressure loss and increase the efficiency and output of
the system 10.
Each transition duct 50 may have an inlet 52, an outlet 54, and a
passage 56 therebetween. The passage 56 defines a combustion
chamber 58 therein, through which the hot gases of combustion flow.
The inlet 52 and outlet 54 of a transition duct 50 may have
generally circular or oval cross-sections, rectangular
cross-sections, triangular cross-sections, or any other suitable
polygonal cross-sections. Further, it should be understood that the
inlet 52 and outlet 54 of a transition duct 50 need not have
similarly shaped cross-sections. For example, in one embodiment,
the inlet 52 may have a generally circular cross-section, while the
outlet 54 may have a generally rectangular cross-section.
Further, the passage 56 may be generally tapered between the inlet
52 and the outlet 54. For example, in an exemplary embodiment, at
least a portion of the passage 56 may be generally conically
shaped. Additionally or alternatively, however, the passage 56 or
any portion thereof may have a generally rectangular cross-section,
triangular cross-section, or any other suitable polygonal
cross-section. It should be understood that the cross-sectional
shape of the passage 56 may change throughout the passage 56 or any
portion thereof as the passage 56 tapers from the relatively larger
inlet 52 to the relatively smaller outlet 54.
The outlet 54 of each of the plurality of transition ducts 50 may
be offset from the inlet 52 of the respective transition duct 50.
The term "offset", as used herein, means spaced from along the
identified coordinate direction. The outlet 54 of each of the
plurality of transition ducts 50 may be longitudinally offset from
the inlet 52 of the respective transition duct 50, such as offset
along the longitudinal axis 90.
Additionally, in exemplary embodiments, the outlet 54 of each of
the plurality of transition ducts 50 may be tangentially offset
from the inlet 52 of the respective transition duct 50, such as
offset along a tangential axis 92. Because the outlet 54 of each of
the plurality of transition ducts 50 is tangentially offset from
the inlet 52 of the respective transition duct 50, the transition
ducts 50 may advantageously utilize the tangential component of the
flow of working fluid through the transition ducts 50 to eliminate
the need for first stage nozzles in the turbine section 16, as
discussed below.
Further, in exemplary embodiments, the outlet 54 of each of the
plurality of transition ducts 50 may be radially offset from the
inlet 52 of the respective transition duct 50, such as offset along
a radial axis 94. Because the outlet 54 of each of the plurality of
transition ducts 50 is radially offset from the inlet 52 of the
respective transition duct 50, the transition ducts 50 may
advantageously utilize the radial component of the flow of working
fluid through the transition ducts 50 to further eliminate the need
for first stage nozzles in the turbine section 16, as discussed
below.
It should be understood that the tangential axis 92 and the radial
axis 94 are defined individually for each transition duct 50 with
respect to the circumference defined by the annular array of
transition ducts 50, as shown in FIG. 3, and that the axes 92 and
94 vary for each transition duct 50 about the circumference based
on the number of transition ducts 50 disposed in an annular array
about the longitudinal axis 90.
As discussed, after hot gases of combustion are flowed through the
transition duct 50, they may be flowed from the transition duct 50
into the turbine section 16. As shown in FIG. 8, a turbine section
16 according to the present disclosure may include a shroud 102,
which may define a hot gas path 104. The shroud 102 may be formed
from a plurality of shroud blocks 106. The shroud blocks 106 may be
disposed in one or more annular arrays, each of which may define a
portion of the hot gas path 104 therein.
The turbine section 16 may further include a plurality of buckets
112 and a plurality of nozzles 114. Each of the plurality of
buckets 112 and nozzles 114 may be at least partially disposed in
the hot gas path 104. Further, the plurality of buckets 112 and the
plurality of nozzles 114 may be disposed in one or more annular
arrays, each of which may define a portion of the hot gas path
104.
The turbine section 16 may include a plurality of turbine stages.
Each stage may include a plurality of buckets 112 disposed in an
annular array and a plurality of nozzles 114 disposed in an annular
array. For example, in one embodiment, the turbine section 16 may
have three stages, as shown in FIG. 7. For example, a first stage
of the turbine section 16 may include a first stage nozzle assembly
(not shown) and a first stage buckets assembly 122. The nozzles
assembly may include a plurality of nozzles 114 disposed and fixed
circumferentially about the shaft 18. The bucket assembly 122 may
include a plurality of buckets 112 disposed circumferentially about
the shaft 18 and coupled to the shaft 18. In exemplary embodiments
wherein the turbine section is coupled to combustor section 14
comprising a plurality of transition ducts 50, however, the first
stage nozzle assembly may be eliminated, such that no nozzles are
disposed upstream of the first stage bucket assembly 122. Upstream
may be defined relative to the flow of hot gases of combustion
through the hot gas path 104.
A second stage of the turbine section 16 may include a second stage
nozzle assembly 123 and a second stage buckets assembly 124. The
nozzles 114 included in the nozzle assembly 123 may be disposed and
fixed circumferentially about the shaft 18. The buckets 112
included in the bucket assembly 124 may be disposed
circumferentially about the shaft 18 and coupled to the shaft 18.
The second stage nozzle assembly 123 is thus positioned between the
first stage bucket assembly 122 and second stage bucket assembly
124 along the hot gas path 104. A third stage of the turbine
section 16 may include a third stage nozzle assembly 125 and a
third stage bucket assembly 126. The nozzles 114 included in the
nozzle assembly 125 may be disposed and fixed circumferentially
about the shaft 18. The buckets 112 included in the bucket assembly
126 may be disposed circumferentially about the shaft 18 and
coupled to the shaft 18. The third stage nozzle assembly 125 is
thus positioned between the second stage bucket assembly 124 and
third stage bucket assembly 126 along the hot gas path 104.
It should be understood that the turbine section 16 is not limited
to three stages, but rather that any number of stages are within
the scope and spirit of the present disclosure.
As further shown in FIGS. 4 through 7, a transition duct 50
according to the present disclosure may include a plurality of
sections, portions, which are articulated with respect to each
other. This articulation of the transition duct 50 may allow the
transition duct 50 to move and shift during operation, allowing for
and accommodating thermal growth thereof. For example, a transition
duct 50 may include an upstream portion 140 and a downstream
portion 142. The upstream portion 140 may include the inlet 52 of
the transition duct 50, and may extend generally downstream
therefrom towards the outlet 54. The downstream portion 142 may
include the outlet 54 of the transition duct 50, and may extend
generally upstream therefrom towards the inlet 52. The upstream
portion 140 may thus include and extend between an inlet end 152
(at the inlet 52) and an aft end 154, and the downstream portion
142 may include and extend between a head end 156 and an outlet end
158 (at the outlet 158).
As shown, a joint 160 may couple the upstream portion 140 and
downstream portion 142 together, and may provide the articulation
between the upstream portion 140 and downstream portion 142 that
allows the transition duct 50 to move during operation of the
turbomachine. Specifically, the joint 160 may couple the aft end
154 and the head end 156 together. The joint 160 may be configured
to allow movement of the upstream portion 140 and the downstream
portion 142 relative to one another about or along at least one
axis. Further, in some embodiments, the joint 160 may be configured
to allow such movement about or along at least two axes, such as
about or along three axes. The axis or axes can be any one or more
of the longitudinal axis 90, the tangential axis 92, and/or the
radial axis 94. Movement about one of these axes may thus mean that
one of the upstream portion 140 or the downstream portion 142 (or
both) can rotate or otherwise move about the axis with respect to
the other due to the joint 160 providing this degree of freedom
between the upstream portion 140 and downstream portion 142.
Movement along one of these axes may thus mean that one of the
upstream portion 140 or the downstream portion 142 (or both) can
translate or otherwise move along the axis with respect to the
other due to the joint 160 providing this degree of freedom between
the upstream portion 140 and downstream portion 142.
In exemplary embodiments as shown in FIGS. 4 through 7, a joint 160
according to the present disclosure includes a generally annular
contact member 162 and a generally annular socket member 164. Each
of the contact member 162 and socket member 164 may be, for
example, a hollow cylinder or ring. The contact member 162, or a
portion thereof, generally fits within the socket member 164, such
that an outer surface 166 of the contact member 162 generally
contacts an inner surface 168 of the socket member 164. The contact
member 162 may generally be movable within the socket member 164,
such as about or along one, two, or three axes, thus providing such
relative movement between the upstream portion 140 and the
downstream portion 142. In exemplary embodiments, as shown, the
contact member 162 may be mounted to the downstream portion 142,
and the socket member 164 may be mounted to the upstream portion
140. In these embodiments, the joint 162 may allow the downstream
portion 142 to move, thus providing the relative movement of the
upstream portion 140 and downstream portion 142. In other
embodiments, the socket member 164 may be mounted to the downstream
portion 142, and the contact member 162 may be mounted to the
upstream portion 140. In these embodiments, the joint 162 may allow
the upstream portion 140 to move, thus providing the relative
movement of the upstream portion 140 and downstream portion
142.
As mentioned, the contact member 162 and socket member 164 are each
mounted to one of the upstream portion 140 and the downstream
portion 142. In some embodiments, the contact member 162 and socket
member 164 are mounted through welding or brazing. Alternatively,
the contact member 162 and socket member 164 may be mounted through
mechanical fastening, such as through use of suitable nut-bolt
combinations, screws, rivets, etc. In still other embodiments, the
contact member 162 and socket member 164 may be mounted by forming
the contact member 162 and socket member 164 integrally with the
upstream portion 140 and the downstream portion 142, such as in a
singular casting procedure. Still further, any suitable mounting
processes and/or apparatus are within the scope and spirit of the
present disclosure.
FIGS. 4 through 7 illustrate one exemplary embodiment of contact
member 162. As shown, the contact member 162 in exemplary
embodiments has a generally curvilinear outer surface 166. Further,
as shown, outer surface 166 may be curved such that the contact
member 162 has a generally arcuate cross-sectional profile. The
arcuate cross-sectional profile may extend along longitudinal axis
90, as shown, or another suitable axis. However, it should be
understood that the present disclosure is not limited to the above
disclosed contact member 162 shapes. Rather, the contact member 162
may have any suitable shape, curvilinear, linear, or otherwise,
that allows for movement of the upstream portion 140 and downstream
portion 142 relative to each other about at least one axis.
FIGS. 4 through 7 additionally illustrate one exemplary embodiment
of a socket member 164. As discussed, the socket member 164 may
accept the contact member 162 therein, such that outer surface 166
of the contact member 162 may contact inner surface 168 of the
socket member 164. As shown, in exemplary embodiments, the inner
surface 168 of the socket member 164 may be generally curvilinear.
Further, the socket member 164 may have a thickness 170. The
thickness 170 may, in exemplary embodiments, increase along the
longitudinal axis 90 in a direction towards the outlet 54 of the
transition duct 50. However, it should be understood that the
present disclosure is not limited to the above disclosed socket
member 164 shapes. Rather, the socket member 164 may have any
suitable shape, curvilinear, linear, or otherwise, that allows for
movement of the transition duct 50 about or along at least one
axis.
As discussed above, the joint 160 may be configured to allow
movement of the upstream portion 140 and downstream portion 142
about at least one axis. Further, in exemplary embodiments, the
joint 160 may be configured to allow such movement about at least
two axes. Still further, in exemplary embodiments, the joint 160
may be configured to allow such movement about three axes. Movement
about an axis as discussed herein generally refers to rotational
movement about the axis. For example, in some embodiments, the
joint 160 may allow movement of the transition duct 50 about the
tangential axis 92. As discussed above, in exemplary embodiments,
the contact member 102 may have a curvilinear and/or arcuate outer
surface 166. During operation of the system 10, the transition duct
50 may experience thermal expansion or other various effects that
may cause the upstream portion 140 and downstream portion 142, such
as the respective aft end 154 and head end 156, to move. The outer
surface 166, in cooperation with the inner surface 168 of the
socket member 164, may allow the transition duct 50 to rotate about
the tangential axis 92, thus preventing stresses in the transition
duct 50. In some embodiments, the contact member 140 may allow such
rotation of the upstream portion 162 relative to the downstream
portion 142, or vice versa, about the tangential axis 92 up to a
maximum of approximately 5 degrees of rotation, or up to a maximum
of 2 degrees of rotation. However, it should be understood that the
present disclosure is not limited to the above disclosed degrees of
rotation, and rather that any suitable rotation of the upstream
portion 140 and downstream portion 142 relative to each other, is
within the scope and spirit of the present disclosure.
Additionally or alternatively, in some embodiments, the joint 160
may allow movement of the transition duct 50 about the radial axis
94. As discussed above, in exemplary embodiments, the contact
member 102 may have a curvilinear and/or arcuate outer surface 166.
During operation of the system 10, the transition duct 50 may
experience thermal expansion or other various effects that may
cause the upstream portion 140 and downstream portion 142, such as
the respective aft end 154 and head end 156, to move. The outer
surface 166, in cooperation with the inner surface 168 of the
socket member 164, may allow the transition duct 50 to rotate about
the radial axis 94, thus preventing stresses in the transition duct
50. In some embodiments, the contact member 140 may allow such
rotation of the upstream portion 162 relative to the downstream
portion 142, or vice versa, about the radial axis 94 up to a
maximum of approximately 5 degrees of rotation, or up to a maximum
of 2 degrees of rotation. However, it should be understood that the
present disclosure is not limited to the above disclosed degrees of
rotation, and rather that any suitable rotation of the upstream
portion 140 and downstream portion 142 relative to each other, is
within the scope and spirit of the present disclosure.
Additionally or alternatively, in some embodiments, the joint 160
may allow movement of the transition duct 50 about the longitudinal
axis 90. As discussed above, in exemplary embodiments, the contact
member 102 may have a curvilinear and/or arcuate outer surface 166.
During operation of the system 10, the transition duct 50 may
experience thermal expansion or other various effects that may
cause the upstream portion 140 and downstream portion 142, such as
the respective aft end 154 and head end 156, to move. The outer
surface 166, in cooperation with the inner surface 168 of the
socket member 164, may allow the transition duct 50 to rotate about
the longitudinal axis 90, thus preventing stresses in the
transition duct 50. In some embodiments, the contact member 140 may
allow such rotation of the upstream portion 162 relative to the
downstream portion 142, or vice versa, about the longitudinal axis
90 up to a maximum of approximately 5 degrees of rotation, or up to
a maximum of 2 degrees of rotation. However, it should be
understood that the present disclosure is not limited to the above
disclosed degrees of rotation, and rather that any suitable
rotation of the upstream portion 140 and downstream portion 142
relative to each other, is within the scope and spirit of the
present disclosure.
Still further, in exemplary embodiments, the joint 160 further
allows movement of the upstream portion 140 and downstream portion
142 relative to each other along at least one axis. Further, in
exemplary embodiments, the joint 160 may be configured to allow
such movement along at least two axes. Still further, in exemplary
embodiments, the joint 160 may be configured to allow such movement
along three axes. Movement along an axis as discussed herein
generally refers to translational movement along the axis. For
example, in some embodiments, the joint 160 may allow movement of
the transition duct 50 along the longitudinal axis 90. For example,
the contact member 162 in exemplary embodiments may be in contact
with the socket member 164 but not mounted or attached to any
surface thereof. Thus, the contact member 162 may slide along the
longitudinal axis 90 if the upstream portion 140 and/or the
downstream portion 142 moves along the longitudinal axis 90, such
as due to thermal expansion or other various effects that may cause
the transition duct 50, such as any portion of the upstream portion
140 and/or downstream portion 142, to move.
Additionally or alternatively, in some embodiments, the joint 160
may allow movement of the transition duct 50 along the tangential
axis 92. For example, the contact member 162 in exemplary
embodiments may be in contact with the socket member 164 but not
mounted or attached to any surface thereof. Thus, the contact
member 162 may slide along the tangential axis 92 if the upstream
portion 140 and/or the downstream portion 142 moves along the
tangential axis 92, such as due to thermal expansion or other
various effects that may cause the transition duct 50, such as any
portion of the upstream portion 140 and/or downstream portion 142,
to move.
Additionally or alternatively, in some embodiments, the joint 160
may allow movement of the transition duct 50 along the radial axis
94. For example, the contact member 162 in exemplary embodiments
may be in contact with the socket member 164 but not mounted or
attached to any surface thereof. Thus, the contact member 162 may
slide along the radial axis 94 if the upstream portion 140 and/or
the downstream portion 142 moves along the radial axis 94, such as
due to thermal expansion or other various effects that may cause
the transition duct 50, such as any portion of the upstream portion
140 and/or downstream portion 142, to move.
This written description uses examples to disclose the invention,
including the best mode, and also to enable any person skilled in
the art to practice the invention, including making and using any
devices or systems and performing any incorporated methods. The
patentable scope of the invention is defined by the claims, and may
include other examples that occur to those skilled in the art. Such
other examples are intended to be within the scope of the claims if
they include structural elements that do not differ from the
literal language of the claims, or if they include equivalent
structural elements with insubstantial differences from the literal
languages of the claims.
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